EP 3339165 B1 20200909 - WING SLAT ACTUATOR DISCONNECTION DETECTION
Title (en)
WING SLAT ACTUATOR DISCONNECTION DETECTION
Title (de)
FLÜGELVORFLÜGELAKTUATORTRENNUNGSERKENNUNG
Title (fr)
DÉTECTION DE DÉSACCOUPLEMENT D'ACTIONNEUR DES BECS DE VOILURE
Publication
Application
Priority
EP 16275181 A 20161222
Abstract (en)
[origin: EP3339165A1] An actuator failure or disconnection detection device (20) for an aircraft leading edge slat (6) comprises a base (22) and a biasing assembly (24) mounted to the base (22) and movable relative thereto. The base (22) and biasing assembly (24) are removably mountable between a fixed structure (202) in the aircraft wing and the slat (6) at an actuator location. The device (20) further comprises an indicator (122) for indicating the amount of movement of the biasing assembly (24) in a direction towards the base (22) when the slat (6) is retracted towards the wing leading edge (4). The indicator (122) may be a collar (120) slidably mounted on the device (20).
IPC 8 full level
B64C 9/22 (2006.01); B64D 45/00 (2006.01); B64F 5/40 (2017.01)
CPC (source: EP US)
B64C 9/22 (2013.01 - EP US); B64C 13/341 (2017.12 - EP US); B64D 45/0005 (2013.01 - EP US); B64F 5/40 (2016.12 - EP US); G07C 5/0816 (2013.01 - US); B64C 3/00 (2013.01 - US); B64C 9/24 (2013.01 - US); B64D 15/12 (2013.01 - US); B64D 2045/001 (2013.01 - EP US); B64F 5/10 (2016.12 - US)
Designated contracting state (EPC)
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
DOCDB simple family (publication)
EP 3339165 A1 20180627; EP 3339165 B1 20200909; CA 2989932 A1 20180622; US 10647444 B2 20200512; US 2018178927 A1 20180628
DOCDB simple family (application)
EP 16275181 A 20161222; CA 2989932 A 20171221; US 201715851805 A 20171222